CN105523172B - Angle of attack control system and angle of attack control method - Google Patents
Angle of attack control system and angle of attack control method Download PDFInfo
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- CN105523172B CN105523172B CN201610013369.5A CN201610013369A CN105523172B CN 105523172 B CN105523172 B CN 105523172B CN 201610013369 A CN201610013369 A CN 201610013369A CN 105523172 B CN105523172 B CN 105523172B
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- 230000005540 biological transmission Effects 0.000 claims description 17
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- 230000009471 action Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
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Abstract
The invention provides a kind of angle of attack control system and angle of attack control method, belong to aircraft field, the angle of attack control system is used for the angle of attack for controlling fixed-wing, fixed-wing is connected with frame, including hinge and angle of attack controlling organization, the cross bar of frame is connected with montant, and montant is connected through the hinge with fixed-wing, and angle of attack controlling organization is used to adjust the angle between fixed-wing and frame.The angle of attack control method employs the angle of attack control system.Angle of attack control system and angle of attack control method provided by the invention can control the angle of attack of fixed-wing by angle of attack controlling organization and hinge, the angle of attack of the aircraft in landing and flight course is adjusted in real time, ensure being normally carried out for landing, ensure smooth flight.
Description
Technical field
The present invention relates to aircraft field, in particular to a kind of angle of attack control system and angle of attack control method.
Background technology
At present, the species of aeromodelling aerocraft is various, such as four-axle aircraft and fixed-wing unmanned plane etc..
Four direction, four rotors around that the rotor of four-axle aircraft is symmetrically distributed in body are in same height
Plane is spent, and the structure of four rotors and radius are all identical, four motors are symmetrically installed on the bracket end of aircraft, in support
Between space lay flight-control computer and external equipment.Four-axle aircraft is turned by adjusting four motor speeds to change rotor
Speed, the change of lift is realized, so as to control the posture of aircraft and position, the electric energy consumed during regulation is bigger,
High energy consumption directly result in cruising time it is short the problem of；Four-axle aircraft flying speed is slow, and middle-size and small-size four axle of higher-end flies at present
The vertical ascent maximal rate of row device is generally 9m/s, and horizontal velocity is maximum to only have 25m/s；Because cruising time is short, flight speed
Degree is slow, causes transport, express delivery, line walking etc. to be all difficult to effectively realize.Most of four-axle aircraft application at present is extremely
Carried out in the confined space, time range.
General fixed-wing model plane are to drive propeller to run at high speed by the motor of head, then provide thrust, when pushing away
When power is more than the frictional resistance of pulley, aircraft will travel forward.Flying speed is very fast, it is necessary to steering in the air for fixed wing aircraft
Hand has good respond, and also stronger operation skill, for multiaxis unmanned plane, operation is more complicated.
Further, since fixed-wing unmanned plane only has the propeller of an offer thrust, and direction is horizontal, in the vertical direction of aircraft
Upper not additional power carrys out the gravity of balance airplane body, the posture of aircraft is adjusted without additional power, so fixed-wing
Can only flight in the air when, using lift caused by wing and empennage and other power, balance could be kept, and sky can not be hovered over
In.
Come in addition, why fixed-wing unmanned plane can fly up, be because the lift of wing overcomes gravity, wing and air
Effect produce lift.The reason for causing wing to act power has two：A, asymmetric aerofoil profile；B, wing and relative wind
There is the angle of attack.Aerofoil profile is the shape of wing profile.Wing profile is mostly asymmetrical type, and the following straight upper arc of arc is bent upwards and upper arc
All it is bent upwards.Symmetrical airfoil then must have certain angle of attack to produce lift.Lift depend mainly on the size of four because
Element:A, lift is directly proportional to wing area；B, lift and air speed is square directly proportional.Under similarity condition, flying speed is got over
Fast lift is bigger；C, lift is relevant with aerofoil profile, and the lift of usual asymmetric aerofoil profile wing is larger；D, lift is relevant with the angle of attack, small
During the angle of attack lift (coefficient) with angle of attack straight line increase, to certain limit after the angle of attack increase lift rapidly reduce on the contrary, this boundary
It is the critical angle of attack.Wing and horizontal displacement also produce resistance in addition to lift is produced, and miscellaneous part typically only produces resistance.
In addition, there is one kind to take into account, VTOL, hovering, flying speed be fast, high-time aircraft, using solid
Determine wing unmanned aerial vehicle body to be engaged with multiaxis propeller, multiaxis pattern, fixed-wing pattern and fixed-wing can be achieved and multiaxis mixes
Syntype, the rotary shaft by rotating the aircraft multiaxis propeller realize the switching of each pattern.In addition, the angle of attack of the aircraft
How to control, turn into the key technology taken off with smooth flight.
The content of the invention
The invention provides a kind of angle of attack control system and angle of attack control method, it is intended to improves above mentioned problem.
What the present invention was realized in：
A kind of angle of attack control system, for controlling the angle of attack of fixed-wing, the fixed-wing is connected with frame, including hinge and
Angle of attack controlling organization, the cross bar of the frame are connected with montant, and the montant passes through the hinge connection, institute with the fixed-wing
Angle of attack controlling organization is stated to be used to adjust the angle between the fixed-wing and the frame.
Further, the angle of attack controlling organization includes control module, lifting drive and lowering or hoisting gear, the control
Molding block and the lifting drive are installed in the frame, and the control module is connected with the lifting drive,
The lifting drive is connected with the lowering or hoisting gear, and the lowering or hoisting gear is connected with the fixed-wing.
Control module control lifting drive work, lifting drive driving lowering or hoisting gear action, lowering or hoisting gear band
One end lifting of dynamic fixed-wing, and fixed-wing is connected through the hinge with montant, then fixed-wing is in lifting around itself and montant
Tie point rotates, and the position of frame is constant, then the angle between fixed-wing and frame changes, it is achieved thereby that fixed-wing
The control of the angle of attack.
Further, the lowering or hoisting gear includes elevating lever and transmission mechanism, and the transmission mechanism drives with the lifting
Device is connected, and the transmission mechanism is connected with the elevating lever, and the elevating lever is connected with the fixed-wing.
Lifting drive drive transmission device, transmission mechanism drive elevating lever, and elevating lever can lift solid so as to drive
One end lifting and around hinge for determining the wing rotate.
Further, the elevating lever is rack, and the transmission mechanism is lifting drive gear, the rack and the liter
Drive gear engagement is dropped, and the one end of the rack away from the lifting drive gear is connected with the fixed-wing.
Under the driving of lifting drive, lifting drive gear is rotated, and band carry-over bar is moved up and down, and rack drives are fixed
One end lifting and around hinge rotation of the wing.The structure coordinated using lifting drive gear and rack, can make lifting quicker,
Stable drive, it is easily controllable.
Further, the elevating lever is sliding block, and the transmission mechanism is screw rod, and the sliding block coordinates with the screw rod,
The one end of the sliding block away from the screw rod is connected with the fixed-wing.
Under the driving of lifting drive, screw rod rotates, while sliding block can be for linear motion along screw rod, so as to band
One end lifting and around hinge rotation of dynamic fixed-wing.The structure being engaged using screw rod and sliding block, lifting can be made steady, be easy to
Control.
Further, the tie point of the elevating lever and the fixed-wing is higher than the pin joint of the hinge, the angle of attack
Controlling organization is arranged between the head of the hinge and the fixed-wing.
When taking off, the pin joint of hinge is higher than by the tie point of angle of attack controlling organization adjustment elevating lever and fixed-wing,
The head of so fixed-wing is lifted up, and positive lift force established angle is formed between fixed-wing and frame, can produce positive lift force.
Further, in addition to lifting connector, the lifting connector include first clamping plate and second clamping plate, the machine
Connecting rod is provided with frame, the connecting rod is fixed between the first clamping plate and the second clamping plate, the control module
It is installed on the lifting drive in the first clamping plate.
By setting first clamping plate and second clamping plate, connecting rod can be firmly clamped in first clamping plate and second clamping plate
Between, and the installation of control module and lifting drive can be made more firm.
Further, the hinge includes hinge connector and rotating shaft, and the rotating shaft is connected with the fixed-wing, the hinge
Bearing is provided with chain fitting, the rotating shaft passes through the bearing, and the montant passes through the hinge connection with the rotating shaft
Part is rotatablely connected.
When rotating, rotating shaft is rotated fixed-wing by bearing, so as to preferably carry out the control of the angle of attack.
Further, the hinge connector includes T-connecting piece and fixed plate, and the bearing is arranged at the T-shaped and connected
On one end of fitting, the montant is fixed between the T-connecting piece and the fixed plate.
By setting T-connecting piece and fixed plate, can firmly by montant be fixed on T-connecting piece and fixed plate it
Between.
Present invention also offers a kind of angle of attack control method, is solved the above problems with auxiliary, the process employs above-mentioned
One angle of attack control system, this method include, and make the fixed-wing by the hinge around described using the angle of attack controlling organization
Montant rotates, to adjust the angle between the fixed-wing and the frame.
The beneficial effect of angle of attack control system and angle of attack control method provided by the invention is：The angle of attack control system passes through
Angle of attack controlling organization adjusts the angle between fixed-wing and frame, and in regulation, fixed-wing is by hinge around its company with montant
Contact rotates, so as to realize the control to the angle of attack of fixed-wing.Angle of attack control system and angle of attack control method provided by the invention
The angle of attack of fixed-wing can be controlled by angle of attack controlling organization and hinge so that aircraft can be in landing and flight course
The angle of attack is adjusted in real time, ensures being normally carried out for landing, ensures smooth flight.
Brief description of the drawings
In order to illustrate the technical solution of the embodiments of the present invention more clearly, below by embodiment it is required use it is attached
Figure is briefly described, it will be appreciated that the following drawings illustrate only certain embodiments of the present invention, therefore be not construed as pair
The restriction of scope, for those of ordinary skill in the art, on the premise of not paying creative work, can also be according to this
A little accompanying drawings obtain other related accompanying drawings.
Fig. 1 is the structural representation for the angle of attack control system that first embodiment of the invention provides；
Fig. 2 is the structural representation of the angle of attack controlling organization for the angle of attack control system that first embodiment of the invention provides；
Fig. 3 is the structural representation of the hinge for the angle of attack control system that first embodiment of the invention provides；
The entirety for the fixed-wing Multi-axis aircraft that Fig. 4 is applied by the angle of attack control system that first embodiment of the invention provides
Structural representation；
Fig. 5 is that the angle of attack control system that first embodiment of the invention provides flies when on fixed-wing Multi-axis aircraft
The one of which state of flight figure of device；
Fig. 6 is that the angle of attack control system that first embodiment of the invention provides flies when on fixed-wing Multi-axis aircraft
Another state of flight figure of device.
Scheming acceptance of the bid note is respectively：
Fixed-wing 101；Frame 102；Hinge 103；Angle of attack controlling organization 104；Cross bar 105；Montant 106；Lifting driving dress
Put 107；Rack 108；Lift drive gear 109；Lift connector 110；First clamping plate 111；Second clamping plate 112；Connecting rod
113；Hinge connector 114；T-connecting piece 115；Fixed plate 116；Rotating shaft 117；Propeller 118；Rotation control mechanism 119；Rotation
Rotating shaft 120.
Embodiment
To make the purpose, technical scheme and advantage of the embodiment of the present invention clearer, below in conjunction with the embodiment of the present invention
In accompanying drawing, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that described embodiment is
Part of the embodiment of the present invention, rather than whole embodiments.The present invention implementation being generally described and illustrated herein in the accompanying drawings
The component of example can be configured to arrange and design with a variety of.Therefore, the reality of the invention to providing in the accompanying drawings below
The detailed description for applying example is not intended to limit the scope of claimed invention, but is merely representative of the selected implementation of the present invention
Example.Based on the embodiment in the present invention, what those of ordinary skill in the art were obtained under the premise of creative work is not made
Every other embodiment, belongs to the scope of protection of the invention.
First embodiment
A kind of angle of attack control system is present embodiments provided, the angle of attack of fixed-wing 101 is controlled on aircraft.This implementation
Example illustrates the structure of the angle of attack control system by taking the application of the angle of attack control system on fixed-wing Multi-axis aircraft as an example
And principle.
Referring to Fig. 1, the fuselage of fixed-wing Multi-axis aircraft is fixed-wing 101, fixed-wing 101 is connected with frame 102, machine
Rotary shaft 120 is provided with frame 102, rotary shaft 120 is with for driving the drive device of propeller 118 to be fixedly connected, driving dress
Put and be connected with propeller 118, propeller 118 is multiple, and each propeller 118 connects a drive device, and drive device is electricity
Machine.Furthermore it is possible to it is that a propeller 118 is equipped with a rotary shaft 120 or a rotary shaft 120 installs multiple spiral shells
Oar 118 is revolved, with four propellers 118, each two is exemplified by totally one rotary shaft 120.In addition, rotation control is provided with frame 102
Mechanism 119 processed, for controlling the rotation of rotary shaft 120.The rotation control mechanism 119 includes control device and travelling gear, passes
In rotary shaft 120, control device is connected moving gear fixed cover with travelling gear by drive mechanism.
The operation principle of the fixed-wing Multi-axis aircraft is：In landing, using multijoint control pattern, propeller 118 is certainly
The rotational plane turned is horizontal, drives the rotation of propeller 118 by drive device, provides lift for aircraft, VTOL causes
Aircraft takeoff is no longer constrained by orographic condition, can complete take off, land in any landform；After the completion of taking off, use
The pattern of fixed-wing 101, rotation control mechanism 119 control rotary shaft 120 to be rotated by 90 °, erect the rotational plane of the rotation of propeller 118
Directly, the rotation of propeller 118 is driven by drive device, thrust is provided for aircraft；In flight course, fixed-wing can be used
101 and multiaxis mixed mode, the rotational angle of the through hole of rotation control mechanism 119 control rotary shaft 120 and coordinate propeller 118
Rotation, control the state of flight of aircraft, there is stable, flexible operating feature.Thus, multiaxis pattern, fixation can be achieved
The pattern of the wing 101 and fixed-wing 101 and multiaxis mixed mode, VTOL, hovering can be taken into account, flying speed is fast, flies
The characteristics of time is long.
Fig. 1 and Fig. 2 are referred to, the angle of attack control system includes hinge 103 and angle of attack controlling organization 104, the horizontal stroke of frame 102
Bar 105 is connected with montant 106, and montant 106 is connected with fixed-wing 101 by hinge 103, and angle of attack controlling organization 104 is used to adjust
Angle between fixed-wing 101 and frame 102.
The angle of attack control system adjusts the angle between fixed-wing 101 and frame 102 by angle of attack controlling organization 104,
During regulation, fixed-wing 101 is rotated by tie point of the hinge 103 around itself and montant 106, so as to realize meeting to fixed-wing 101
The control at angle.Angle of attack control system provided by the invention can control fixed-wing by angle of attack controlling organization 104 and hinge 103
101 angle of attack so that aircraft can be adjusted in real time in the angle of attack in landing and flight course, ensure normally entering for landing
OK, smooth flight is ensured.
Refer to Fig. 1, Fig. 4~Fig. 6, the angle of attack Control System Design of fixed-wing Multi-axis aircraft so that aircraft is flying
Held stationary flies in row mode transfer process.From the transfer process for vertically rising to horizontal flight, first with multijoint control
Pattern, four entirety of propellers 118 are turned forward, start flight forward, four motors are same during rotating forward
In one plane.Multiaxis oar causes the angle of attack to reduce, passes through angle of attack control system towards aircraft can be caused integrally to lean forward during top rake
Control adjust the change in angle of attack caused by transfer process.When needing to change the angle of attack in flight course, the angle of attack can be passed through
Control system adjusts the angle of attack.Fixation can be switched to when the speed of flight reaches when fixed-wing 101 can produce enough lift
The offline mode of the wing 101.
Fig. 1 and Fig. 2 are referred to, angle of attack controlling organization 104 includes control module, lifting drive 107 and lifting dress
Put, control module and lifting drive 107 are installed in frame 102, and control module is connected with lifting drive 107, are risen
Drop drive device 107 is connected with lowering or hoisting gear, and lowering or hoisting gear is connected with fixed-wing 101.
Control module control lifting drive 107 works, and lifting drive 107 drives lowering or hoisting gear action, lifting
Device drives one end lifting of fixed-wing 101, and fixed-wing 101 is connected with montant 106 by hinge 103, then fixed-wing 101
Tie point in lifting around itself and montant 106 rotates, and the position of frame 102 is constant, then between fixed-wing 101 and frame 102
Angle change, it is achieved thereby that the control of the angle of attack of fixed-wing 101.
Fig. 1 and Fig. 2 are referred to, lowering or hoisting gear includes elevating lever and transmission mechanism, transmission mechanism and lifting drive 107
Connection, transmission mechanism are connected with elevating lever, and elevating lever is connected with fixed-wing 101.
The drive transmission device of lifting drive 107, transmission mechanism drive elevating lever, and elevating lever can be lifted so as to drive
Simultaneously around hinge 103 rotates for one end lifting of fixed-wing 101.
Referring to Fig. 2, elevating lever is rack 108, transmission mechanism is lifting drive gear 109, and rack 108 drives with lifting
Gear 109 is engaged, and the one end of rack 108 away from lifting drive gear 109 is connected with fixed-wing 101.
Under the driving of lifting drive 107, lifting drive gear 109 rotates, and band carry-over bar 108 moves up and down, tooth
Bar 108 drives one end lifting of fixed-wing 101 and around hinge 103 rotates.Coordinated using lifting drive gear 109 and rack 108
Structure, lifting can be made quicker, stable drive is easily controllable.
In addition, elevating lever can also be sliding block, transmission mechanism can also be screw rod (diagram is not shown), and sliding block is matched somebody with somebody with screw rod
Close, the one end of sliding block away from screw rod is connected with fixed-wing 101.Under the driving of lifting drive 107, screw rod rotates, simultaneously
Sliding block can be for linear motion along screw rod, and so as to drive, one end of fixed-wing 101 lifts and around hinge 103 rotates.Using spiral shell
The structure that bar and sliding block are engaged, lifting can be made steady, be easy to control.
Referring to Fig. 1, the tie point of elevating lever and fixed-wing 101 is higher than the pin joint of hinge 103, angle of attack controlling organization
104 are arranged between the head of hinge 103 and fixed-wing 101.
When taking off, the tie point that elevating lever and fixed-wing 101 are adjusted by angle of attack controlling organization 104 is higher than hinge 103
Pin joint, the head of such fixed-wing 101 is lifted up, and forms that " positive lift force is pacified between fixed-wing 101 and frame 102
Fill angle ", positive lift force can be produced.
" positive lift force established angle " design of fixed-wing Multi-axis aircraft so that aircraft is protected in offline mode transfer process
Hold smooth flight.From the transfer process for vertically rising to horizontal flight, with multijoint control pattern, multiaxis oar towards top rake,
Fly forward.Multiaxis oar certainly will cause aircraft integrally to lean forward the negative angle of attack of generation towards top rake, hinder wing to produce positive lift force.
Initial settling angle and the design of the adjustable angle of attack, multiaxis forward leaning angle is taken into account, wing is had when mounted with multi-axle planar
Larger established angle, ensure that wing can still produce positive lift force when leaning forward flight, overcome what multiaxis merged with fixed-wing 101
Contradiction.Enough horizontal velocities are obtained with multiaxis offline mode, when reaching flying speed requirement, then switch to the mould of fixed-wing 101
Formula, so as to ensure that by multiaxis pattern switching into the pattern of fixed-wing 101 it is steady with it is safe.It is from the patten transformation of fixed-wing 101
Multiaxis pattern and the process landed, then it is under the pattern of fixed-wing 101, opens multiaxis pattern, gradually reduce flying speed,
Reduce lift caused by wing and gradually substituted by rotor lift, after the completion of multiaxis pattern takes over fixed-wing 101, with multiaxis pattern
Realize vertical landing.Positive lift force established angle is manually adjustable, to the position of needs.
Referring to Fig. 2, the angle of attack control system also includes lifting connector 110, lifting connector 110 includes first clamping plate
111 and second clamping plate 112, connecting rod 113 is provided with frame 102, and connecting rod 113 is fixed on the folder of first clamping plate 111 and second
Between plate 112, control module and lifting drive 107 are installed in first clamping plate 111.
By setting first clamping plate 111 and second clamping plate 112, connecting rod 113 can be firmly clamped in first clamping plate
Between 111 and second clamping plate 112, and the installation of control module and lifting drive 107 can be made more firm.
Referring to Fig. 3, hinge 103 includes hinge connector 114 and rotating shaft 117, rotating shaft 117 is connected with fixed-wing 101, hinge
It is provided with bearing on chain fitting 114, rotating shaft 117 passes through bearing, and montant 106 and rotating shaft 117 part 114 that is connected through the hinge rotate
Connection.
When rotating, rotating shaft 117 is rotated fixed-wing 101 by bearing, so as to preferably carry out the control of the angle of attack.
Referring to Fig. 3, hinge connector 114 includes T-connecting piece 115 and fixed plate 116, bearing is arranged at T-shaped connection
On one end of part 115, montant 106 is fixed between T-connecting piece 115 and fixed plate 116.
By setting T-connecting piece 115 and fixed plate 116, montant 106 firmly can be fixed on T-connecting piece 115
Between fixed plate 116.
Hinge connector 114 is two, and the both ends of rotating shaft 117 are connected with fixed-wing 101 respectively, the cross bar 105 of frame 102
For two, every cross bar 105 is connected with a montant 106, and two hinge connectors 114 are respectively connected with a montant 106.
Using two hinge connectors 114, the both ends for being capable of countershaft 117 are played a supporting role so that 101 turns of fixed-wing
It is dynamic steady, make the control of the angle of attack and regulation more accurate.
Second embodiment
A kind of angle of attack control method is present embodiments provided, the process employs the angle of attack that first embodiment provides to control system
System, this method include, and fixed-wing 101 is rotated by hinge around montant 106 using angle of attack controlling organization 104, to adjust fixation
Angle between the wing 101 and frame 102.
Specifically, control module control lifting drive 107 works, and lifting drive 107 drives lowering or hoisting gear
Action, lowering or hoisting gear drives one end lifting of fixed-wing 101, and fixed-wing 101 is connected with montant 106 by hinge 103, then
Fixed-wing 101 rotates in lifting around the tie point of itself and montant 106, and the position of frame 102 is constant, then fixed-wing 101 and machine
Angle between frame 102 changes, it is achieved thereby that the control of the angle of attack of fixed-wing 101.
Under the driving of lifting drive 107, lifting drive gear 109 rotates, and band carry-over bar 108 moves up and down, tooth
Bar 108 drives one end lifting of fixed-wing 101 and around hinge 103 rotates.So as to realize the control of the angle of attack.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", " on ", " under ", "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer ", " up time
The orientation or position relationship of the instruction such as pin ", " counterclockwise " are based on orientation shown in the drawings or position relationship, are for only for ease of
Description is of the invention to be described with simplified, rather than the equipment or element of instruction or hint meaning must be with specific orientation, Yi Te
Fixed azimuth configuration and operation, therefore be not considered as limiting the invention.
In addition, term " first ", " second " are only used for describing purpose, and it is not intended that instruction or hint relative importance
Or the implicit quantity for indicating indicated technical characteristic.Thus, define " first ", the feature of " second " can be expressed or
Implicitly include one or more this feature.In the description of the invention, " multiple " are meant that two or more,
Unless otherwise specifically defined.
In the present invention, unless otherwise clearly defined and limited, term " installation ", " connected ", " connection ", " fixation " etc.
Term should be interpreted broadly, for example, it may be fixedly connected or be detachably connected, or integrally；Can be that machinery connects
Connect or electrically connect；Can be joined directly together, can also be indirectly connected by intermediary, can be in two elements
The connection in portion or the interaction relationship of two elements.For the ordinary skill in the art, can be according to specific feelings
Condition understands the concrete meaning of above-mentioned term in the present invention.
In the present invention, unless otherwise clearly defined and limited, fisrt feature second feature it " on " or it " under "
Can directly it be contacted including the first and second features, it is not directly to contact but pass through it that can also include the first and second features
Between other characterisation contact.Moreover, fisrt feature second feature " on ", " top " and " above " to include first special
Sign is directly over second feature and oblique upper, or is merely representative of fisrt feature level height and is higher than second feature.Fisrt feature exists
Second feature " under ", " lower section " and " following " fisrt feature that includes are immediately below second feature and obliquely downward, or be merely representative of
Fisrt feature level height is less than second feature.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the invention, for the skill of this area
For art personnel, the present invention can have various modifications and variations.Within the spirit and principles of the invention, that is made any repaiies
Change, equivalent substitution, improvement etc., should be included in the scope of the protection.
Claims (8)
1. a kind of angle of attack control system, for controlling the angle of attack of fixed-wing, the fixed-wing is connected with frame, it is characterised in that
Including hinge and angle of attack controlling organization, the cross bar of the frame is connected with montant, and the montant passes through described with the fixed-wing
Hinge connection, the angle of attack controlling organization are used to adjust the angle between the fixed-wing and the frame；
The angle of attack controlling organization includes control module, lifting drive and lowering or hoisting gear, the control module and described
Lifting drive is installed in the frame, and the control module is connected with the lifting drive, the lifting driving
Device is connected with the lowering or hoisting gear, and the lowering or hoisting gear is connected with the fixed-wing；
The angle of attack control system also includes lifting connector, and the lifting connector includes first clamping plate and second clamping plate, institute
State and connecting rod is provided with frame, the connecting rod is fixed between the first clamping plate and the second clamping plate, the control
Module and the lifting drive are installed in the first clamping plate.
2. angle of attack control system according to claim 1, it is characterised in that the lowering or hoisting gear includes elevating lever and transmission
Mechanism, the transmission mechanism are connected with the lifting drive, and the transmission mechanism is connected with the elevating lever, the lifting
Bar is connected with the fixed-wing.
3. angle of attack control system according to claim 2, it is characterised in that the elevating lever is rack, the driver
Structure is lifting drive gear, and the rack engages with the lifting drive gear, and the rack is away from the lifting drive gear
One end be connected with the fixed-wing.
4. angle of attack control system according to claim 2, it is characterised in that the elevating lever is sliding block, the driver
Structure is screw rod, and the sliding block coordinates with the screw rod, and the one end of the sliding block away from the screw rod is connected with the fixed-wing.
5. angle of attack control system according to claim 2, it is characterised in that the connection of the elevating lever and the fixed-wing
Point is higher than the pin joint of the hinge, and the angle of attack controlling organization is arranged between the head of the hinge and the fixed-wing.
6. angle of attack control system according to claim 1, it is characterised in that the hinge includes hinge connector and turned
Axle, the rotating shaft are connected with the fixed-wing, and bearing is provided with the hinge connector, and the rotating shaft passes through the bearing,
The montant is rotatablely connected with the rotating shaft by the hinge connector.
7. angle of attack control system according to claim 6, it is characterised in that the hinge connector includes T-connecting piece
And fixed plate, the bearing are arranged on one end of the T-connecting piece, the montant is fixed on the T-connecting piece and institute
State between fixed plate.
8. a kind of angle of attack control method, it is characterised in that employ the angle of attack control system as described in claim any one of 1-7
System, this method include：The fixed-wing is set to be rotated by the hinge around the montant using the angle of attack controlling organization, to adjust
Save the angle between the fixed-wing and the frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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| CN106965933A (en) * | 2017-03-10 | 2017-07-21 | 佛山市神风航空科技有限公司 | The launching apparatus and mode of a kind of aircraft |
| CN111434585B (en) * | 2019-01-12 | 2023-06-09 | 上海航空电器有限公司 | Aviation five-state attack angle indication and landing indication control system and method |
| CN113048118B (en) * | 2021-03-24 | 2022-02-18 | 大连理工大学 | Hydraulic supporting device for adjusting attack angle |
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| US5509623A (en) * | 1994-06-15 | 1996-04-23 | Freewing Aerial Robotics Corporation | Free wing aircraft having a free wing used as an air brake to shorten roll-out following touchdown |
| CN1660668A (en) * | 2004-02-24 | 2005-08-31 | 陈启星 | Attack angle changeable aircraft wing |
| CN201951711U (en) * | 2010-10-18 | 2011-08-31 | 南京航空航天大学 | Tilting mechanism |
| CN203944127U (en) * | 2014-07-01 | 2014-11-19 | 王领军 | Wing model aircraft wing whirligig verts |
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